Mitsubishi Heavy Industries Limited

Dai Nippon Printing Co., Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Hitachi, Ltd.

Mitsubishi Power, Ltd.

Dai Nippon Printingco., Ltd.

Keisuke Miura

Tomomi Koganezawa

Satoshi Dodo

Yusuke Hagiwara

Kazuki Abe

Takeo Saito

Kazuhito Koyama

Norio Ishii

Hiroshi Inoue

Yoshitaka Hirata

Tomo Kawakami

Shinichi Fukuba

Makoto Yamaki

Keijiro Saito

Kenta Taniguchi

Tomohiro Asai

Tomoya Kawashima

Satoshi Kumagai

Mitsuhiro Karishuku

Yasunori Hayashida

Satoshi Takiguchi

Akinori Hayashi

Tsubasa Honda

Noriko Katashima

Hirokazu Takahashi

Yusuke Nakamura

Kenji Miyamoto

Yoshihide Wadayama

Kiyoshi Fujimoto

Katsuyoshi Tada

Koji Eto

Shohei Yoshida

Hiromi Koizumi

Minoru Azakami

Yukinori Katagiri

Yoshitaka Terada

Yasuhiro Akiyama

Nobuko Oikawa

Yoshinori Matsubara

Tatsuya Hagita

Takao Ikezawa

Keita Yunoki

Shota Igarashi

Hiroyuki Takeishi

Noboru Okuyama

Satoru Nishima

Takehiko Nishikawa

Eriko Hamade

Shohei Uramoto

Tomoya Murota

Yuki Kamikawa

Shingo Yoshida

Yusuke Nushi

Taku Egawa

Zhi Zhang

A combustor of the present disclosure includes a combustor plate configured to have a downstream end face perpendicular to a combustor axis; a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and a plurality of second nozzles configured to inject the fuel from the downstream end face. A plurality of the nozzles segments are provided at intervals in a direction perpendicular to the combustor axis. Each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face.

Combustor and gas turbine

A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each of the at least one fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each of the at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protruding portion. A top surface of the protruding portion includes a convex curved surface.

Burner assembly, gas turbine combustor, and gas turbine

A combustor includes a plurality of fuel nozzles installed so as to be extended in a direction of a nozzle axis and configured to inject fuel toward one side in the direction of the nozzle axis, a pipe plate having a plurality of air holes formed therein so as to be extended in the direction of the nozzle axis, in which the air hole has an inner diameter larger than a tip end portion of the fuel nozzle and the tip end portions are respectively inserted into the air holes, and a step surface formed at a position of the tip end portion closer to the other side in the direction of the nozzle axis than a tip end surface of the tip end portion so as to be expanded in a radial direction with respect to the nozzle axis from a tip end outer peripheral surface.

A combustor includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which an air hole passing through the upstream side end face and the downstream side end face is formed in the tube plate; and a fuel injector that injects fuel into air passing through the air hole. The air hole has: a bent channel that curves toward a direction orthogonal to the combustor axis toward the downstream side; and an inclined channel that is connected to the downstream side of the bent channel so as to be continuous therewith, and that extends inclining with respect to the combustor axis and opens to the downstream side end face. A fuel injection position at which the fuel injector injects fuel is located on the downstream side of the upstream end of the bent channel.

This gas turbine equipment comprises a gas turbine and a control device. A combustor of the gas turbine uses ammonia as fuel, and uses the RQL method. A compressor of the gas turbine includes an intake adjustor that adjusts an intake rate which is the flow rate of air that flows into a compressor casing. When the concentration of NOx in exhaust gas reaches or exceeds a predetermined value, the control device controls the operation of the intake adjustor so that the intake rate decreases.

Gas turbine equipment with compressor airflow control responsive to NOx concentration and control method thereof

Provided are a laminated glass which has a reduced occurrence of voids and accumulation of liquid crystal, and a production method for the laminated glass. Also provided is a laminated glass which can prevent deterioration of a sealing material. This laminated glasscomprises a first glass plateA, a first intermediate filmA, a liquid crystal film, a second intermediate filmB, and a second glass plate, which are layered and disposed in this order, wherein the first glass plateA and the second glass plateB have a larger outer shape than that of the liquid crystal film, and a spaceris provided in at least a portion of a region which is interposed between the first glass plateA and the second glass plateB and in which the liquid crystal filmis not disposed.

Laminated glass and production method for laminated glass

A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

Provided is a light control film capable of gradually changing the in-plane transmittance and thereby adding an in-plane gradation between light and dark. A light control filmaccording to the present invention includes: a first electrodeA and a second electrodeB disposed facing each other; a light control materialdisposed between the first electrodeA and the second electrodeB and changing the transmittance in accordance with the potential difference between the first electrodeA and the second electrodeB; and a potential gradient forming part for providing the gradient of the potential difference in the extension direction of the first electrodeA and the second electrodeB.

Light control film, method for driving light control film, light control member, and vehicle

The present invention is to enable avoidance of a reduction in external appearance quality, and stable driving, and prevent diffracted light from being discerned by avoiding a reduction in transmittance and a deterioration in liquid crystal alignment. A light control film is provided with: a first laminate in which an alignment layer is provided; a second laminate in which an alignment layer is provided; a liquid crystal layer which is sandwiched between the first and second laminates and contains liquid crystal molecules; a spacer disposed in the liquid crystal layer to hold the thickness of the liquid crystal layer; and electrodes provided in the first laminate and/or the second laminate, and controls transmitted light by controlling the alignment of the liquid crystal molecules driven by the electrodes. The proportion of an area occupied by the spacer per unit area in a light controllable-region of the liquid crystal layer is 0.1-10%.

Light transmission control film and laminated glass

A gas turbine combustor includes a burner composed of a fuel nozzle group having a plurality of fuel nozzles for fuel supply, a fuel nozzle plate structurally supporting the fuel nozzles and serving to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate located downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least a proximal end of the outer circumferential fuel nozzles is larger than that of the inner circumferential fuel nozzles.

Gas turbine combustor

A method for manufacturing a laminated glass whereby, in a laminated glass comprising a liquid crystal film sandwiched therein and having a three-dimensionally curved surface shape, the formation of wrinkles in the liquid crystal film can be suppressed; and a laminated glass which has a three-dimensionally curved surface shape and in which wrinkles in a liquid crystal film sandwiched therein are suppressed. The method for manufacturing the laminated glass comprises: a heat molding step for heating the liquid crystal film to a temperature higher than the glass transition point of the first base material layer and the second base material layer; and a bonding step for, after completing the heat molding step, heating the laminate, wherein the liquid crystal film is sandwiched between the first glass sheet and the second glass sheet, at a temperature lower than the glass transition point and bonding the same by applying a preset pressure.

Method for manufacturing laminated glass, laminated glass and light control film

[Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

Fuel nozzle of gas turbine combustor and manufacturing method thereof, and gas turbine combustor

To suppress separation of air flows in air holes that are positioned in the outermost circumferential row in an air hole plate, but are far from a turn guide. A gas turbine combustor includes: an inner cylinder forming a combustion chamber; an outer cylinder forming a cylindrical outer circumference flow path through which compressed air flows, between the outer cylinder and the inner cylinder; an end cover closing an end portion of the outer cylinder; an air hole plate having air holes introducing the compressed air passed through the outer circumference flow path, into the combustion chamber; a plurality of fuel nozzles injecting a fuel into the combustion chamber via the air holes; a turn guide provided to the inner cylinder or the air hole plate and guiding a turn of the compressed air passed through the outer circumference flow path; and an auxiliary guide provided at an outer circumferential portion of a surface of the air hole plate facing the fuel nozzles, so as to be positioned on an inner circumference side with respect to the turn guide.

Gas turbine combustor, and gas turbine

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Yokohama, Japan

Keisuke Miura